Feed of exhaust gases to turbosuperchargers



A. P. E. PLANIOL FEED 0F EXHAUST GASES-T0 TURBO SUPERCHARQERS Filed Oct.9, 1941 INVENTOR.

ANDRE PAUL EUQENE PLAN/0L a 4 M mg,

ATTOR vs Patented July 3, 1945 FEED OF EXHAUST GASES TTURBOSUPERCH'ARGERS Andr Paul Eugene Planiol, Huntington, Y.

Application October 9, 1941, Serial No. 414,328.

. In France February 10, 1941 2 Claims.

The use of the exhaust gases of airplane engines to operate turbinesordinarily causes difll- (Chill-.6)

the exhaust turbine the gases pass to the atmosphere through a tube 9.As the airplane is flying culties of a thermal nature due to theexcessive temperature of these gases which produces a prematuredestruction of pipes, collectors and rotating vanes of theturbo-machines.

This invention is characterized primarily by the provision of a heatexchanger comprising a plurality of tubes which is placed in adivergent,

convergent enclosure traversed by a stream of air,

' of the tubes.

heat exchanger before entering the turbine. The Y invention includesalso the production of a supplementary propelling efiect for'theairplane.

In other words, according to the invention there is interposed betweenthe-exhaust collector of the engine and the inlet of the turbine one orseveral cooling equipments for the exhaust gases which are placed insuch a way that the heat yielded by the exhaust gases tothe ambient airisused to aid in propulsion of the airplane.

By lowering the temperature of the exhaust gases the energy of theexhaust gases available for actuating the turbine is necessarily reducedbut this loss of energy is not-wasted because of the useful propellingeffect obtained from the use of the heat exchanger as hereinafterdescribed. This heat exchanger constitutes a thermal machine of reactionof a known type where heat originates in the exhaust gases travelingfrom the engine to the turbine. The thermal machine of reaction receivesat one end the air coming from the atmosphere compressedby the relativespeed of the plane. Thereafter this air is heated by contact with thetubes of the exchanger which are in contact on their outer surfaces withthe air and on their inner surfaces with the exhaust gases of hightemperature. The thus heated air is directed to the rear and allowed toexpand, thus increasing its speed and aidingin the propulsion of theplane.

The accompanying drawing illustrates one embodiment of the invention. I

In accordance with the invention a heat exchanger I is positioned withinan open ended from right to left of the drawing, air enters chamber 3 inthe direction of the arrow I0 and passes about the tubes of the radiatorl to cool the exhaust gases before admission to the turbine and in turnto be heated by contact with the walls As the heat exchanger I ispreferably so positioned as to occasion but slight loss in pressure ofthe air in passing from chamber 3 to chamber 6, the increase in airtemperature will result in expansion of the air in the chamber 4 andthis work of expansion will be transferred nearly entirely into kineticenergy. The final temperature being-higher than the initial temair). Theexcess of the kinetic energy betweenthe outlet andthe inlet provides themotive powor developed by the system. It is quite obvious that theenclosure 2 may be positioned either outside of the body of the plane soas to receive the atmospheric air, orit may be placed at another part ofthe plane as, for example, in the wings or fuselage or adjacent theengines; the,

"ing the aircraft engine, if the turbo-machinehas a sufficiently higho'utput,and if also the turbine can resist sufilciently hightemperature, that the energy of the gases rendered available by the ex-40 pansion to atmospheric pressure exceeds what is necessary to operatethe turbine. In this case it would be advantageous, rather than toreduce the pressure of the exhaust gases in the heat exchanger I by morethan is needed for the correct functioning of. the machine, to providethe exhaust pipes of'the turbine with a nozzle ll directed to the rearand thus communicate a high speed to the gases passingfrom the turbine;the

resulting kinetic energy creates a motive impulsion and'the expansion ofthe exhaust gases is thus achieved in two separate steps, first in theturbine and second in the reaction nozzle II. The propelling emciency ofthis nozzle is of course greater the greater the speed of the airplaneThe following is claimed:

1. The combination in an airplane having an engine and an exhaustturbine operated by the exhaust gases thereof, of a heat exchangerinserted between the engine and the turbine for passage of the exhaustgases therethrough, and an open ended divergent-convergent enclosurecontaining said exchanger and positioned for passage of air therethroughin the direction of flight of the plane, said exchanger being sopositioned within said enclosure as to occasion but slight loss inpressure of the air in passing from the divergent to the convergentportion of the enclosure, whereby the exhaust gases are cooled prior tointroduction into the turbine and the air stream is heated by the gasesand the increased kinetic energy of the air stream gives a propulsioneffect to the plane.

2. The combination according to claim 1 including a rearwardly directedconvergent nozzle for delivery of the exhaust gases from the turbine 10to the atmosphere.

